YS-900 (ys900-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 50,000 Max Cl/Cd: 17.28 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys900-il-50000.txt Download as CSV file: xf-ys900-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5831 0.10133 0.09487 -0.0021 1.0000 0.3469
-8.250 -0.5817 0.09835 0.09192 0.0008 1.0000 0.3747
-8.000 -0.5901 0.09619 0.08985 0.0043 1.0000 0.4046
-6.750 -0.5246 0.07971 0.07343 0.0194 1.0000 0.5809
-6.500 -0.5713 0.07679 0.07071 0.0204 1.0000 0.5356
-6.250 -0.6231 0.07280 0.06693 0.0208 1.0000 0.4895
-6.000 -0.6616 0.06991 0.06419 0.0247 1.0000 0.4775
-5.750 -0.7008 0.06636 0.06074 0.0275 1.0000 0.4618
-5.500 -0.7390 0.06292 0.05730 0.0299 1.0000 0.4454
-5.250 -0.7502 0.05595 0.04946 0.0201 1.0000 0.3065
-5.000 -0.7248 0.05046 0.04249 0.0178 1.0000 0.1712
-4.750 -0.7008 0.04686 0.03799 0.0205 1.0000 0.1252
-4.500 -0.6801 0.04404 0.03416 0.0240 1.0000 0.1012
-4.250 -0.6585 0.04109 0.03064 0.0268 1.0000 0.0879
-4.000 -0.6353 0.03809 0.02709 0.0291 1.0000 0.0782
-3.750 -0.6092 0.03558 0.02418 0.0307 1.0000 0.0724
-3.500 -0.5790 0.03314 0.02124 0.0318 1.0000 0.0668
-3.250 -0.2022 0.02582 0.01536 -0.0243 1.0000 1.0000
-3.000 -0.1874 0.02552 0.01457 -0.0222 1.0000 1.0000
-2.750 -0.1727 0.02525 0.01394 -0.0202 1.0000 1.0000
-2.500 -0.1577 0.02501 0.01341 -0.0183 1.0000 1.0000
-2.250 -0.1425 0.02481 0.01295 -0.0164 1.0000 1.0000
-2.000 -0.1273 0.02463 0.01258 -0.0145 1.0000 1.0000
-1.750 -0.1117 0.02448 0.01225 -0.0127 1.0000 1.0000
-1.500 -0.0960 0.02435 0.01197 -0.0108 1.0000 1.0000
-1.250 -0.0802 0.02425 0.01177 -0.0090 1.0000 1.0000
-1.000 -0.0642 0.02416 0.01153 -0.0072 1.0000 1.0000
-0.750 -0.0482 0.02410 0.01138 -0.0054 1.0000 1.0000
-0.500 -0.0322 0.02405 0.01127 -0.0036 1.0000 1.0000
-0.250 -0.0161 0.02403 0.01120 -0.0018 1.0000 1.0000
0.000 0.0001 0.02402 0.01118 0.0000 1.0000 1.0000
0.250 0.0162 0.02403 0.01120 0.0017 1.0000 1.0000
0.500 0.0323 0.02406 0.01126 0.0035 1.0000 1.0000
0.750 0.0483 0.02410 0.01137 0.0053 1.0000 1.0000
1.000 0.0643 0.02417 0.01153 0.0071 1.0000 1.0000
1.250 0.0803 0.02425 0.01174 0.0089 1.0000 1.0000
1.500 0.0961 0.02436 0.01196 0.0108 1.0000 1.0000
1.750 0.1117 0.02448 0.01223 0.0126 1.0000 1.0000
2.000 0.1272 0.02463 0.01255 0.0144 1.0000 1.0000
2.250 0.1426 0.02481 0.01293 0.0163 1.0000 1.0000
2.500 0.1577 0.02502 0.01337 0.0182 1.0000 1.0000
2.750 0.1726 0.02525 0.01388 0.0201 1.0000 1.0000
3.000 0.1873 0.02552 0.01452 0.0221 1.0000 1.0000
3.250 0.2021 0.02583 0.01530 0.0242 1.0000 1.0000
3.500 0.2169 0.02615 0.01623 0.0264 1.0000 1.0000
3.750 0.6086 0.03521 0.02377 -0.0309 0.0720 1.0000
4.000 0.6366 0.03857 0.02732 -0.0301 0.0768 1.0000
4.250 0.6586 0.04057 0.03014 -0.0269 0.0869 1.0000
4.500 0.6803 0.04347 0.03364 -0.0241 0.1001 1.0000
4.750 0.7012 0.04631 0.03744 -0.0208 0.1220 1.0000
5.000 0.7229 0.05006 0.04202 -0.0178 0.1623 1.0000
5.250 0.7529 0.05548 0.04896 -0.0195 0.2896 1.0000
5.500 0.7430 0.06167 0.05596 -0.0271 0.4165 1.0000
5.750 0.7096 0.06676 0.06118 -0.0294 0.4722 1.0000
6.000 0.6708 0.07081 0.06513 -0.0278 0.4978 1.0000
6.250 0.6290 0.07316 0.06732 -0.0224 0.4996 1.0000
6.500 0.5807 0.07627 0.07023 -0.0197 0.5214 1.0000
7.500 0.4561 0.08080 0.07487 -0.0035 0.4664 1.0000
7.750 0.5874 0.09330 0.08701 -0.0088 0.4449 1.0000
8.000 0.5748 0.09510 0.08872 -0.0045 0.4110 1.0000
8.250 0.5906 0.09869 0.09231 -0.0013 0.3774 1.0000
8.500 0.5891 0.10149 0.09505 0.0017 0.3499 1.0000
8.750 0.5933 0.10464 0.09829 0.0045 0.3241 1.0000
9.000 0.6047 0.10850 0.10214 0.0073 0.2992 1.0000
9.250 0.5887 0.11080 0.10433 0.0086 0.2836 1.0000
9.500 0.5837 0.11354 0.10701 0.0099 0.2674 1.0000
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Polar data table (+)
Polar graphs
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